TEMPORARY REVISION RJ/242
Vol. 1
Page 1 of 1
TEMPORARY REVISION RJ/242
Oct 29/09
LETTER OF TRANSMITTAL
REASON FOR ISSUE
Vol. 1
Page 1 of 1
Oct 29/09
LETTER OF TRANSMITTAL
REASON FOR ISSUE
Temporary revision to advise the flight crew of the following:
Temporary revision to advise the flight crew of the following:
S Changes to Performance Penalties for Operation with Airplane Systems Inoperative.
S Changes to Performance Penalties for Operation with Airplane Systems Inoperative.
INSTRUCTIONS FOR INSERTION OF THIS TEMPORARY REVISION
INSTRUCTIONS FOR INSERTION OF THIS TEMPORARY REVISION
1.
Insert the Record of Temporary Revisions in the front portion of the Flight Crew
Operating Manual, Vol. 1.
1.
Insert the Record of Temporary Revisions in the front portion of the Flight Crew
Operating Manual, Vol. 1.
2.
Remove and destroy the following pages from the Flight Crew Operating Manual, Vol. 2
and replace them with appropriate (yellow-coloured) pages from this package:
S 07--25--1 <MASTER> and 07--25--2 <MASTER>, and
2.
Remove and destroy the following pages from the Flight Crew Operating Manual, Vol. 2
and replace them with appropriate (yellow-coloured) pages from this package:
S 07--25--1 <MASTER> and 07--25--2 <MASTER>, and
S 07--25--5 <MASTER> thru 07--25--8 <MASTER>.
S 07--25--5 <MASTER> thru 07--25--8 <MASTER>.
3.
Record the insertion of this Temporary Revision on the Record of Temporary Revisions
page.
3.
Record the insertion of this Temporary Revision on the Record of Temporary Revisions
page.
4.
Retain this page for record purposes.
4.
Retain this page for record purposes.
LIST OF PAGES AFFECTED BY THIS TEMPORARY REVISION
S Volume 2:
LIST OF PAGES AFFECTED BY THIS TEMPORARY REVISION
S Volume 2:
S 07--25--2 <MASTER>,
S 07--25--5 <MASTER>, and
S 07--25--8 <MASTER>.
S 07--25--2 <MASTER>,
S 07--25--5 <MASTER>, and
S 07--25--8 <MASTER>.
Flight Crew Operating
Manual
CSP A -- 013
Flight Crew Operating
Manual
CSP A -- 013
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
1.
2.
Vol. 2
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
07--25--1
REV 58, Oct 31/05
INTRODUCTION
1.
INTRODUCTION
This supplement is applicable only when used in conjunction with a Minimum Equipment List
approved by the appropriate authority.
The data in this supplement provide performance corrections to be applied when dispatching
with specific airplane systems inoperative.
The data in this supplement provide performance corrections to be applied when dispatching
with specific airplane systems inoperative.
These data complement or supersede data contained in the basic Airplane Flight Manual.
This supplement must therefore be used in conjunction with the basic Airplane Flight
Manual.
These data complement or supersede data contained in the basic Airplane Flight Manual.
This supplement must therefore be used in conjunction with the basic Airplane Flight
Manual.
The effect of this supplement on the basic Airplane Flight Manual is given in paragraphs 2.
to 7.
The effect of this supplement on the basic Airplane Flight Manual is given in paragraphs 2.
to 7.
LIMITATIONS
2.
LIMITATIONS
The limitations in Volume 1, Chapter 2 are applicable, except as modified by the following:
The limitations in Volume 1, Chapter 2 are applicable, except as modified by the following:
A.
A.
B.
Integrated Drive Generator (IDG) 1 or 2 Inoperative
C.
Engine-Driven Pump (EDP) 1 or 2 Inoperative
B.
AC Hydraulic Pump 1 Inoperative
C.
AC Hydraulic Pump 2 Inoperative
D.
EMERGENCY PROCEDURES
3.
EMERGENCY PROCEDURES
The emergency procedures in Volume 1, Chapter 3 are applicable.
NORMAL PROCEDURES
4.
The normal procedures in Volume 1, Chapter 4 are applicable.
NORMAL PROCEDURES
The normal procedures in Volume 1, Chapter 4 are applicable.
ABNORMAL PROCEDURES
5.
The abnormal procedures in Volume 1, Chapter 5 are applicable.
ABNORMAL PROCEDURES
The abnormal procedures in Volume 1, Chapter 5 are applicable.
PERFORMANCE
6.
The performance data given in Volume 2/3, Chapter 6 are applicable, except as modified by
the following:
Flight Crew Operating Manual
CSP A--013
AC Hydraulic Pump 2 Inoperative
S The minimum flight weight is 17,464 kg (38,500 lb).
S Take-offs and landings on contaminated runways are prohibited.
The emergency procedures in Volume 1, Chapter 3 are applicable.
6.
AC Hydraulic Pump 1 Inoperative
S The minimum flight weight is 17,464 kg (38,500 lb).
S The minimum flight weight is 17,464 kg (38,500 lb).
S Take-offs and landings on contaminated runways are prohibited.
5.
Engine-Driven Pump (EDP) 1 or 2 Inoperative
S The minimum flight weight is 17,464 kg (38,500 lb).
S The minimum flight weight is 17,464 kg (38,500 lb).
D.
Integrated Drive Generator (IDG) 1 or 2 Inoperative
S The minimum flight weight is 17,464 kg (38,500 lb).
S The minimum flight weight is 17,464 kg (38,500 lb).
4.
07--25--1
REV 58, Oct 31/05
This supplement is applicable only when used in conjunction with a Minimum Equipment List
approved by the appropriate authority.
S The minimum flight weight is 17,464 kg (38,500 lb).
3.
Vol. 2
MASTER
PERFORMANCE
The performance data given in Volume 2/3, Chapter 6 are applicable, except as modified by
the following:
Flight Crew Operating Manual
CSP A--013
MASTER
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
Vol. 2
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
07--25--2
TR RJ/242, Oct 29/09
NOTE
The following take-off performance corrections are
applicable to dry or wet runway performance data for
airplanes equipped with either CF34-3A1 or CF34-3B1
engines.
A.
07--25--2
TR RJ/242, Oct 29/09
NOTE
The following take-off performance corrections are
applicable to dry or wet runway performance data for
airplanes equipped with either CF34-3A1 or CF34-3B1
engines.
AC Hydraulic Pump 1 Inoperative
A.
AC Hydraulic Pump 1 Inoperative
With the AC hydraulic pump 1 inoperative, adjust the performance data as follows:
With the AC hydraulic pump 1 inoperative, adjust the performance data as follows:
Minimum Control Speed, Ground (VMCG):
Minimum Control Speed, Ground (VMCG):
VMCG (Flaps 8˚)
100 KIAS (100 KCAS)
VMCG (Flaps 8˚)
100 KIAS (100 KCAS)
VMCG (Flaps 20˚)
100 KIAS (100 KCAS)
VMCG (Flaps 20˚)
100 KIAS (100 KCAS)
Minimum V1 Limited by Control on the Ground (V1MCG):
Minimum V1 Limited by Control on the Ground (V1MCG):
V1MCG (Flaps 8˚)
105 KIAS (105 KCAS)
V1MCG (Flaps 8˚)
105 KIAS (105 KCAS)
V1MCG (Flaps 20˚)
105 KIAS (105 KCAS)
V1MCG (Flaps 20˚)
105 KIAS (105 KCAS)
When determining the field length limited take-off weight and V1 speed:
Available accelerate-stop distance
When determining the field length limited take-off weight and V1 speed:
Reduce by 4%
Available accelerate-stop distance
For a planned take-off weight, when determining the required accelerate-stop distance:
B.
Vol. 2
Required accelerate-stop distance
Increase by 4%
Landing field length, Flaps 45_
Increase by 9%
AC Hydraulic Pump 2 Inoperative
Reduce by 4%
For a planned take-off weight, when determining the required accelerate-stop distance:
B.
Required accelerate-stop distance
Increase by 4%
Landing field length, Flaps 45_
Increase by 9%
AC Hydraulic Pump 2 Inoperative
With the AC hydraulic pump 2 inoperative, adjust the performance data as follows:
With the AC hydraulic pump 2 inoperative, adjust the performance data as follows:
Minimum Control Speed, Ground (VMCG):
Minimum Control Speed, Ground (VMCG):
VMCG (Flaps 8˚)
100 KIAS (100 KCAS)
VMCG (Flaps 8˚)
100 KIAS (100 KCAS)
VMCG (Flaps 20˚)
100 KIAS (100 KCAS)
VMCG (Flaps 20˚)
100 KIAS (100 KCAS)
Minimum V1 Limited by Control on the Ground (V1MCG):
Minimum V1 Limited by Control on the Ground (V1MCG):
V1MCG (Flaps 8˚)
105 KIAS (105 KCAS)
V1MCG (Flaps 8˚)
105 KIAS (105 KCAS)
V1MCG (Flaps 20˚)
105 KIAS (105 KCAS)
V1MCG (Flaps 20˚)
105 KIAS (105 KCAS)
When determining the field length limited take-off weight and V1 speed:
Available accelerate-stop distance
See paragraph 6. B. (1)
For a planned take-off weight, when determining the required accelerate-stop distance:
When determining the field length limited take-off weight and V1 speed:
Available accelerate-stop distance
See paragraph 6. B. (1)
For a planned take-off weight, when determining the required accelerate-stop distance:
Required accelerate-stop distance
See paragraph 6. B. (2)
Required accelerate-stop distance
See paragraph 6. B. (2)
Landing field length, Flaps 45_
See paragraph 6. B. (4)
Landing field length, Flaps 45_
See paragraph 6. B. (4)
Flight Crew Operating Manual
CSP A-- 013
MASTER
Flight Crew Operating Manual
CSP A--013
MASTER
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
(3)
Vol. 2
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
07--25--5
TR RJ/242, Oct 29/09
MAXIMUM V1 LIMITED BY BRAKE ENERGY (V1MBE)
(3)
LANDING FIELD LENGTH, FLAPS 45_
S
S
The Maximum V1 Speed Limited by Brake Energy (V1MBE) derived from Chapter
6: PERFORMANCE --- TAKE-OFF PERFORMANCE --- TAKE-OFF SPEEDS, must
be reduced by 42 KIAS.
(4)
Effectivity:
07--25--5
TR RJ/242, Oct 29/09
MAXIMUM V1 LIMITED BY BRAKE ENERGY (V1MBE)
The Maximum V1 Speed Limited by Brake Energy (V1MBE) derived from Chapter
6: PERFORMANCE --- TAKE-OFF PERFORMANCE --- TAKE-OFF SPEEDS, must
be reduced by 42 KIAS.
(4)
Vol. 2
LANDING FIELD LENGTH, FLAPS 45_
Effectivity:
Airplanes without the reduced rudder travel modification; and
Airplanes not incorporating Service Bulletin SB 601R--27--081, Flight Controls--Rudder, Reduced
Rudder Travel.
S
S
The landing field length required for various conditions of airplane weight, airport
pressure altitude, wind and runway condition, with the AC hydraulic pump 2
inoperative is provided on Figure 07---25---3. The actual landing distance on a dry
runway is equal to the dry runway landing field length multiplied by 0.6. Figure
07---25---3 is applicable to airplanes equipped with CF34-3A1 engines <type spec>.
Airplanes without the reduced rudder travel modification; and
Airplanes not incorporating Service Bulletin SB 601R--27--081, Flight Controls--Rudder, Reduced
Rudder Travel.
The landing field length required for various conditions of airplane weight, airport
pressure altitude, wind and runway condition, with the AC hydraulic pump 2
inoperative is provided on Figure 07---25---3. The actual landing distance on a dry
runway is equal to the dry runway landing field length multiplied by 0.6. Figure
07---25---3 is applicable to airplanes equipped with CF34-3A1 engines <type spec>.
Example:
Example:
Associated conditions:
Landing gross weight = 18,000 kg (39,700 lb)
Airport pressure altitude = 6,000 feet
Wind
= 20 knots, headwind
Runway condition
= Wet
Associated conditions:
Landing gross weight = 18,000 kg (39,700 lb)
Airport pressure altitude = 6,000 feet
Wind
= 20 knots, headwind
Runway condition
= Wet
Enter the chart at the gross weight scale, for the above-mentioned conditions to obtain
the landing field length of 2,770 meters (9,080 feet).
Enter the chart at the gross weight scale, for the above-mentioned conditions to obtain
the landing field length of 2,770 meters (9,080 feet).
Effectivity: <0005><0048><0073>
S
S
Effectivity: <0005><0048><0073>
Airplanes with the reduced rudder travel modification; and
Airplanes incorporating Service Bulletin SB 601R--27--081, Flight Controls--Rudder, Reduced
Rudder Travel.
S
S
Airplanes with the reduced rudder travel modification; and
Airplanes incorporating Service Bulletin SB 601R--27--081, Flight Controls--Rudder, Reduced
Rudder Travel.
The landing field length required for various conditions of airplane weight, airport
pressure altitude, wind and runway condition, with the AC hydraulic pump 2 inoperative
is provided on Figure 07---25---4. The actual landing distance on a dry runway is equal
to the dry runway landing field length multiplied by 0.6. Figure 07---25---4 is applicable
to airplanes equipped with CF34-3A1 engines <0048><0073> / CF34-3B1 engines <0005>.
The landing field length required for various conditions of airplane weight, airport
pressure altitude, wind and runway condition, with the AC hydraulic pump 2 inoperative
is provided on Figure 07---25---4. The actual landing distance on a dry runway is equal
to the dry runway landing field length multiplied by 0.6. Figure 07---25---4 is applicable
to airplanes equipped with CF34-3A1 engines <0048><0073> / CF34-3B1 engines <0005>.
Example:
Example:
Associated conditions:
Landing gross weight = 18,000 kg (39,700 lb)
Airport pressure altitude = 6,000 feet
Wind
= 20 knots, headwind
Runway condition
= Wet
Enter the chart at the gross weight scale, for the above-mentioned conditions to
obtain the landing field length of 2,730 meters (8,950 feet).
Associated conditions:
Landing gross weight = 18,000 kg (39,700 lb)
Airport pressure altitude = 6,000 feet
Wind
= 20 knots, headwind
Runway condition
= Wet
Enter the chart at the gross weight scale, for the above-mentioned conditions to
obtain the landing field length of 2,730 meters (8,950 feet).
Flight Crew Operating Manual
CSP A-- 013
MASTER
Flight Crew Operating Manual
CSP A-- 013
MASTER
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
Vol. 2
07--25--6
REV 58, Oct 31/05
Landing Field Length -- Flaps 45_ <type spec>
Vol. 2
07--25--6
REV 58, Oct 31/05
Landing Field Length -- Flaps 45_ <type spec>
Figure 07---25---3
Flight Crew Operating Manual
CSP A-- 013
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
Figure 07---25---3
MASTER
Flight Crew Operating Manual
CSP A--013
MASTER
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
07--25--7
Vol. 2
REV 58, Oct 31/05
Effectivity: <0005><0048><0073>
S Airplanes with the reduced rudder travel modification; and
S Airplanes incorporating Service Bulletin SB 601R ---27 ---081, Flight Controls ---Rudder, Reduced Rudder Travel.
Landing Field Length -- Flaps 45_ <MST>
07--25--7
Vol. 2
REV 58, Oct 31/05
Effectivity: <0005><0048><0073>
S Airplanes with the reduced rudder travel modification; and
S Airplanes incorporating Service Bulletin SB 601R ---27 ---081, Flight Controls ---Rudder, Reduced Rudder Travel.
Landing Field Length -- Flaps 45_ <MST>
Figure 07---25---4
Flight Crew Operating Manual
CSP A--013
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
Figure 07---25---4
MASTER
Flight Crew Operating Manual
CSP A--013
MASTER
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
Vol. 2
SUPPLEMENTARY PROCEDURES
Performance Penalties for Operation
With Airplane Systems Inoperative
07--25--8
TR RJ/242, Oct 29/09
S The landing approach speed (VREF) should be derived from Chapter 6:
C.
C.
Take-off weight limited by field length
Reduce by 3%
Take-off weight limited by field length
Reduce by 3%
Increase by 6%
Take-off and accelerate-stop distance
Increase by 6%
Take-off weight limited by climb or obstacle
clearance requirements
Maximum landing weight limited by climb
requirements
First segment, second segment, final segment,
enroute approach and landing climb gradient
Reduce by 6%
Reduce by 6%
Reduce by 1%
Nose Wheel Steering Inoperative
With nose wheel steering inoperative, adjust the performance data as follows:
Take-off distance and accelerate-stop distance
D.
Available accelerate-stop distance and the
available runway length
Reduce by 6%
Reduce by 1%
Increase by 2%
When determining the field length limited take-off weight and V1 speed:
Available accelerate-stop distance and the
available runway length
Reduce by 2%
Ground Spoilers Inoperative
With one pair of inboard or outboard ground spoilers inoperative, adjust the
performance data as follows:
E.
When determining the field length limited take-off weight and V1 speed:
Available accelerate-stop distance
Reduce by 6%
Nose Wheel Steering Inoperative
With nose wheel steering inoperative, adjust the performance data as follows:
Take-off distance and accelerate-stop distance
Increase by 2%
When determining the field length limited take-off weight and V1 speed:
Reduce by 2%
Ground Spoilers Inoperative
With one pair of inboard or outboard ground spoilers inoperative, adjust the
performance data as follows:
When determining the field length limited take-off weight and V1 speed:
Reduce by 4%
Available accelerate-stop distance
For a planned take-off weight, when determining the required accelerate-stop distance:
7.
Reduce by 1.5%
S Use cowl and wing anti-ice performance and adjust performance data as follows:
Take-off and accelerate-stop distance
Take-off weight limited by climb or obstacle
clearance requirements
Maximum landing weight limited by climb
requirements
First segment, second segment, final segment,
enroute approach and landing climb gradient
E.
PERFORMANCE -- LANDING PERFORMANCE -- LANDING FIELD LENGTH
AND SPEED.
Engine Cowl Anti-ice Pressure Relief Valve Inoperative
If cowl or wing and cowl anti-ice is on with one cowl anti-ice pressure relief valve
inoperative:
S Use cowl and wing anti-ice performance data, and adjust the performance data as
follows:
Thrust settings (N1)
Reduce by 1.5%
S Use cowl and wing anti-ice performance and adjust performance data as follows:
D.
07--25--8
TR RJ/242, Oct 29/09
S The landing approach speed (VREF) should be derived from Chapter 6:
PERFORMANCE -- LANDING PERFORMANCE -- LANDING FIELD LENGTH
AND SPEED.
Engine Cowl Anti-ice Pressure Relief Valve Inoperative
If cowl or wing and cowl anti-ice is on with one cowl anti-ice pressure relief valve
inoperative:
S Use cowl and wing anti-ice performance data, and adjust the performance data as
follows:
Thrust settings (N1)
Vol. 2
Reduce by 4%
For a planned take-off weight, when determining the required accelerate-stop distance:
Required accelerate-stop distance
Increase by 4%
Required accelerate-stop distance
Increase by 4%
Landing field length, Flaps 45_
Increase by 9%
Landing field length, Flaps 45_
Increase by 9%
SUPPLEMENTS
The supplementary data in Chapter 7 remain unchanged and applicable unless otherwise
indicated by the following paragraph.
S Use of this Supplement in conjunction with other approved Supplements shall be
accomplished in accordance with the Master Minimum Equipment List.
Flight Crew Operating Manual
CSP A-- 013
MASTER
7.
SUPPLEMENTS
The supplementary data in Chapter 7 remain unchanged and applicable unless otherwise
indicated by the following paragraph.
S Use of this Supplement in conjunction with other approved Supplements shall be
accomplished in accordance with the Master Minimum Equipment List.
Flight Crew Operating Manual
CSP A-- 013
MASTER